Aiming at the study of wake vortex hazard zone, which can effectively avoid the occurrence of rear wake vortex danger encounter events, a wake vortex danger area method based on lidar detection data was proposed. According to the measured data of Li-DAR, the evolution trajectory and velocity loop of the aircraft wake vortex were inverted. Based on the aerodynamic response of the rear engine to the front tail vortex, a rolling torque coefficient model was constructed. Considering the evolution of the tail vortex in the actual scene, combined with the characteristic parameters of the tail vortex obtained by inversion, the rolling torque of the aircraft when encountering the tail vortex was calculated and the tail vortex danger zone was estimated. The results show that the tail vortex characteristic parameters are obtained based on lidar detection data inversion, and the position, height and ring amount of the left vortex and the right vortex are not consistent. The danger zone calculated by combining the rolling torque coefficient model also has asymmetry, and when the ring amount of the single vortex is larger, the corresponding danger zone is also larger. For a tail vortex with a left vortex (390 m, 8.61°), right vortex (435 m, 8.85°) at the coordinate position. The ring quantities of the left vortex and the right vortex are 256.83 m²/s and 223.35 m²/s respectively. The actual danger zone of the right vortex has a larger range, so the interval between the rear machine and the front machine can be adjusted differently, which is conducive to putting forward an important reference for analyzing the safety of the rear machine and shortening the wake interval.